U.S. patent number 11,428,190 [Application Number 16/914,782] was granted by the patent office on 2022-08-30 for grid-type thrust reverser for turbojet engine.
This patent grant is currently assigned to Safran Nacelles. The grantee listed for this patent is Safran Nacelles. Invention is credited to Patrick Boileau, Benjamin Brebion, Loic Grall, Sebastien Michel Thierry Guillemant, Alexis Heau, Melody Seriset.
United States Patent |
11,428,190 |
Grall , et al. |
August 30, 2022 |
Grid-type thrust reverser for turbojet engine
Abstract
A grid-type thrust reverser for a turbojet engine includes a
moving O-shaped thrust reverser body that is generally cylindrical
in shape around a longitudinal central axis (A) and includes an
inner wall configured to delimit a cold air stream, with an inner
structure that surrounds the turbojet engine, the movable thrust
reverser body being mounted so as to be able to slide along the
longitudinal central axis (A) between a direct jet position in
which the outer cowl covers the thrust reverser grids, and a
thrust-reversal position in which the outer cowl uncovers the
thrust reverser grids. The movable thrust reverser body includes a
first half-portion and a second half-portion that are mounted so as
to each pivot about a longitudinal pivot axis (B), between a closed
position and an open gullwing position for removing the turbojet
engine, via the cradle.
Inventors: |
Grall; Loic (Gonfreville
l'Orcher, FR), Heau; Alexis (Gonfreville l'Orcher,
FR), Brebion; Benjamin (Gonfreville l'Orcher,
FR), Guillemant; Sebastien Michel Thierry
(Gonfreville l'Orcher, FR), Seriset; Melody
(Gonfreville l'Orcher, FR), Boileau; Patrick
(Gonfreville l'Orcher, FR) |
Applicant: |
Name |
City |
State |
Country |
Type |
Safran Nacelles |
Gonfreville l'Orcher |
N/A |
FR |
|
|
Assignee: |
Safran Nacelles (Gonfreville
l'Orcher, FR)
|
Family
ID: |
1000006531603 |
Appl.
No.: |
16/914,782 |
Filed: |
June 29, 2020 |
Prior Publication Data
|
|
|
|
Document
Identifier |
Publication Date |
|
US 20210079871 A1 |
Mar 18, 2021 |
|
Related U.S. Patent Documents
|
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
Issue Date |
|
|
PCT/FR2018/053463 |
Dec 20, 2018 |
|
|
|
|
Foreign Application Priority Data
|
|
|
|
|
Dec 28, 2017 [FR] |
|
|
17/63328 |
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64D
29/06 (20130101); F02K 1/70 (20130101); B64D
29/08 (20130101); F02K 1/80 (20130101); F05D
2240/129 (20130101); F05D 2220/323 (20130101) |
Current International
Class: |
F02K
1/70 (20060101); B64D 29/08 (20060101); B64D
29/06 (20060101); F02K 1/80 (20060101) |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
2129901 |
|
Dec 2009 |
|
EP |
|
2907759 |
|
May 2008 |
|
FR |
|
2911372 |
|
Jul 2008 |
|
FR |
|
2019036053 |
|
Feb 2019 |
|
WO |
|
Other References
International Search Report for International Application
PCT/FR2018/053463, dated Apr. 10, 2019. cited by applicant.
|
Primary Examiner: Nguyen; Andrew H
Attorney, Agent or Firm: Burris Law, PLLC
Parent Case Text
CROSS-REFERENCE TO RELATED APPLICATIONS
This application is a continuation of International Application No.
PCT/FR2018/053463, filed on Dec. 20, 2018, which claims priority to
and the benefit of FR 17/63328 filed on Dec. 28, 2017. The
disclosures of the above applications are incorporated herein by
reference.
Claims
What is claimed is:
1. A cascade thrust reverser for a turbojet engine configured to
form at least one portion of a downstream section of a nacelle
accommodating the turbojet engine, the cascade thrust reverser
comprising: a front frame adapted to be mounted downstream of a fan
casing and supporting thrust reverser cascades; an O-type thrust
reverser movable body having a cylindrical shape around a
longitudinal central axis and comprising an inner wall adapted to
delimit a cold air flow path with an inner structure, the cold flow
path devoid of any connecting portions extending therethrough, the
inner structure surrounding the turbojet engine, and an outer cowl,
the O-type thrust reverser movable body being slidably mounted
along the longitudinal central axis between a direct jet position
in which the outer cowl covers the thrust reverser cascades, and a
thrust reversal position in which the outer cowl uncovers the
thrust reverser cascades; and a cradle which is configured to link
an upper portion of the O-type thrust reverser movable body on a
suspension pylon of the nacelle to provide sliding of the O-type
thrust reverser movable body, wherein the O-type thrust reverser
movable body comprises a first half-portion and a second
half-portion, each of the first half-portion and the second
half-portion being semi-cylindrical and linked to one another in a
lower portion of the O-type thrust reverser movable body by a first
dismountable link device, each of the first half-portion and the
second half-portion of the O-type thrust reverser movable body
being pivotally mounted about a longitudinal pivot axis, between a
closed position and a butterfly open position for removing the
turbojet engine, via the cradle.
2. The cascade thrust reverser according to claim 1, wherein the
outer cowl of the O-type thrust reverser movable body comprises a
C-shaped first half-cowl and a C-shaped second half-cowl, each of
the C-shaped first half-cowl and the C-shaped second half-cowl
being pivotally mounted about a longitudinal pivot axis C, between
a closed position and a maintenance butterfly open position.
3. The cascade thrust reverser according to claim 1, further
comprising a second dismountable link device which slidably links
the thrust reverser cascades on the O-type thrust reverser movable
body.
4. The cascade thrust reverser according to claim 3, wherein the
second dismountable link device is a screw-nut type dismountable
link device.
5. The cascade thrust reverser according to claim 1, wherein the
first dismountable link device is a screw-nut type dismountable
link device.
6. The cascade thrust reverser according to claim 1, wherein the
cradle comprises: a first half-cradle carrying the first
half-portion of the O-type thrust reverser movable body and
pivotally mounted on the suspension pylon about the longitudinal
pivot axis B of the first half-portion configured to provide
pivoting of the first half-portion of the O-type thrust reverser
movable body; and a second half-cradle carrying the second
half-portion of the O-type thrust reverser movable body and
pivotally mounted on the suspension pylon about the longitudinal
pivot axis of the second half-portion so as to provide pivoting of
the second half-portion of the O-type thrust reverser movable
body.
7. The cascade thrust reverser according to claim 6, wherein the
cascade thrust reverser comprises an anti-rotation device
configured to pivotally lock the first half-portion and the second
half-portion of the O-type thrust reverser movable body in the
closed position, and wherein the anti-rotation device comprises: a
first lock which locks the first half-cradle pivotally on the
suspension pylon; and a second lock which locks the second
half-cradle pivotally on the suspension pylon.
8. The cascade thrust reverser according to claim 6, wherein the
first half-cradle comprises a slide connection which slidably links
the first half-portion of the O-type thrust reverser movable body
on the suspension pylon, and the second half-cradle comprises a
slide connection which slidably links the second half-portion of
the O-type thrust reverser movable body on the suspension
pylon.
9. The cascade thrust reverser according to claim 1, wherein the
cascade thrust reverser comprises an anti-rotation device
configured to pivotally lock the first half-portion and the second
half-portion of the O-type thrust reverser movable body in the
closed position.
10. The cascade thrust reverser according to claim 1, wherein the
cascade thrust reverser comprises a plurality of actuators, each
actuator of the plurality of actuators linking the front frame of
the thrust reverser on the thrust reverser cascades and configured
to slidably drive the thrust reverser cascades and the O-type
thrust reverser movable body.
11. The cascade thrust reverser according to claim 1, wherein the
O-type thrust reverser movable body is detached from the inner
structure.
12. A nacelle for an aircraft turbojet engine comprising a cascade
thrust reverser according to claim 1.
Description
FIELD
The present disclosure relates to a cascade thrust reverser for a
turbojet engine intended to form at least one portion of a
downstream section of a nacelle accommodating the turbojet engine.
More particularly, the present disclosure concerns an O-type thrust
reverser.
BACKGROUND
The statements in this section merely provide background
information related to the present disclosure and may not
constitute prior art.
In general, an aircraft is propelled by several turbojet engines
each housed within a nacelle accommodating a set of auxiliary
actuation devices relating to its operation and providing various
functions when the turbojet engine is running or shut down.
In particular, these auxiliary actuation devices comprise a thrust
reverser device.
A turbojet engine nacelle generally has a substantially tubular
structure comprising an air inlet upstream of the turbojet engine,
a middle section intended to surround a fan of the turbojet engine,
a downstream section intended to surround the combustion chamber of
the turbojet engine and possibly integrating thrust reversal means,
and generally terminates in an ejection nozzle whose outlet is
located downstream of the turbojet engine.
Modern nacelles are intended to accommodate a bypass turbojet
engine adapted to generate through the blades of the rotating fan a
hot air flow (primary flow) and a cold air flow (secondary flow)
which circulates outside the turbojet engine through an annular
passage, also called flow path, formed between a fairing of the
turbojet engine and an inner wall of the nacelle. Both air flows
are ejected from the turbojet engine by the rear of the
nacelle.
During the landing of the aircraft, the function of a thrust
reverser device is to improve the braking capability thereof by
forwardly redirecting at least one portion of the air ejected by
the turbojet engine. In this phase, the thrust reverser device
obstructs at least one portion of the cold air flow path and
directs this flow toward the front of the nacelle, thereby
generating a counter-thrust which is added to the braking of the
wheels and air-brakes of the aircraft.
In the case of a cascade thrust reverser, the deflection of the
cold air flow is performed by cascade vanes, associated to thrust
reverser flaps brought to block at least partially the circulation
flow path of the cold flow.
There are known at least two types of thrust reversers, a D-type
thrust reverser, called "D duct," and an O-type thrust reverser,
called "O duct."
Typically, the D-type thrust reverser includes two half-structures,
with a substantially semi-cylindrical shape, as shown in this FIG.
1.
The two D-shaped half-structures form an Outer Fixed Structure
(OFS) and a concentric Inner Fixed Structure (IFS), surrounding a
downstream section of the turbojet engine accommodating the gas
generator, or engine, of the turbojet engine.
The inner and outer fixed structures define the flow path intended
to channel the cold air flow that circulates outside the turbojet
engine.
In addition, each half-structure carries a D-shaped half-cowl, the
C-shaped half-cowls being slidably mounted between a direct jet
position in which the half-cowls cover the thrust reverser
cascades, and a thrust reversal position in which the half-cowls
uncover the thrust reverser cascades.
Also, the two half-structures are pivotally mounted in a butterfly
fashion on the pylon at the upper portion (at 12 O'clock) by hinges
parallel to the longitudinal axis of the nacelle, between a closed
position and a maintenance butterfly open position in order to
enable access to the gas generator during maintenance
operations.
This so-called D-type thrust reverser facilitates access to the
turbojet engine when the two half-structures are open in a
butterfly fashion in the maintenance open position and enable quick
removal of the turbojet engine.
The O-type thrust reverser comprises a thrust reverser movable body
in one single portion without any interruption at the lower
portion, such a structure is described for example in French Patent
No. FR 2 911 372.
The thrust reverser movable body has a generally cylindrical shape
around a longitudinal axis and comprises an inner wall adapted to
delimit the cold air flow path with an inner structure which
surrounds the turbojet engine.
Thus, the sliding thrust reverser movable body is dissociated from
the inner structure surrounding the engine.
The thrust reverser movable body also comprises an outer cowl.
The thrust reverser movable body is slidably mounted on the
suspension pylon, along a longitudinal axis, between a direct jet
position in which the outer cowl covers the thrust reverser
cascades, a thrust reversal position in which the outer cowl
uncovers the thrust reverser cascades.
A drawback of the O-type thrust reverser is the time period for a
turbojet engine change operation.
Indeed, the turbojet engine change operation requires the removal
of the thrust reverser movable body on a carriage, this removal
being time-consuming.
Conversely, the absence of obstacle in the cold air flow path of
the O-type thrust reverser improves the aerodynamic performance and
the fuel consumption of the aircraft while enhancing the
effectiveness of the thrust reverser.
Indeed, the D-type thrust reverser includes a connection,
referenced as 9 in FIG. 1, between the inner structure and the
inner structure, which extends in the cold air flow path.
SUMMARY
This section provides a general summary of the disclosure and is
not a comprehensive disclosure of its full scope or all of its
features.
The present disclosure aims in particular at providing a thrust
reverser which combines the advantages of both types of thrust
reversers presented hereinabove.
The present disclosure relates to a cascade thrust reverser for a
turbojet engine intended to form at least one portion of a
downstream section of a nacelle accommodating a turbojet engine,
the thrust reverser including a front frame which is adapted to be
mounted downstream of a fan casing and which supports thrust
reverser cascades, an O-type thrust reverser movable body which has
a generally cylindrical shape around a longitudinal central axis
and which comprises an inner wall adapted to delimit a cold air
flow path with an inner structure which surrounds the turbojet
engine, and an outer cowl, the O-type thrust reverser movable body
being slidably mounted along a longitudinal central axis between a
direct jet position in which the outer cowl covers the thrust
reverser cascades, a thrust reversal position in which the outer
cowl uncovers the thrust reverser cascades, and a cradle which is
designed so as to link an upper portion of the O-type thrust
reverser movable body on a suspension pylon of the nacelle in order
to provide sliding of the O-type thrust reverser movable body. The
O-type thrust reverser movable body comprises a first half-portion
and a second half-portion each being generally semi-cylindrical and
are linked to one another in a lower portion of the O-type thrust
reverser movable body, by a first dismountable link device, each of
the first half-portion and second half-portion of the O-type thrust
reverser movable body being pivotally mounted about a longitudinal
pivot axis, between a closed position and a butterfly open position
for removing the turbojet engine, via the cradle.
The thrust reverser according to the present disclosure allows
combining the advantages of an O-shaped structure and the
advantages of a D-shaped structure.
Indeed, the cold air flow path delimited by the O-type thrust
reverser movable body is devoid of any connecting portions
extending through the cold air flow path.
In addition, the O-type thrust reverser movable body according to
the present disclosure is designed so as to occupy a butterfly open
position which enables removal of the turbojet engine without
having to remove the O-type thrust reverser movable body.
According to another form of the present disclosure, the outer cowl
of the O-type thrust reverser movable body includes C-shaped first
half-cowl and second half-cowl each being pivotally mounted about a
longitudinal pivot axis, between a closed position and a
maintenance butterfly open position.
Through its opening, the outer cowl allows accessing the turbojet
engine for maintenance tasks.
According to yet another form of the present disclosure, a second
dismountable link device slidably links the cascade vanes on the
O-type thrust reverser movable body in a dismountable way.
This feature allows detaching the assembly formed by the thrust
reverser cascades and the actuators, from the assembly formed by
the O-type thrust reverser movable body.
According to another feature, the second dismountable link device
is of the screw-nut type.
According to another feature, the first dismountable link device is
of the screw-nut type.
According to another feature, the cradle includes a first
half-cradle which carries the first half-portion of the O-type
thrust reverser movable body and which is pivotally mounted on the
pylon about the pivot axis of the first half-portion so as to
provide pivoting of the first half-portion of the O-type thrust
reverser movable body, and a second half-cradle which carries the
second half-portion of the O-type thrust reverser movable body and
which is pivotally mounted on the pylon about the pivot axis of the
second half-portion so as to provide pivoting of the second
half-portion of the O-type thrust reverser movable body.
According to another feature, the thrust reverser includes an
anti-rotation device which is designed so as to pivotally lock the
first half-portion and the second half-portion of the O-type thrust
reverser movable body in their closed position.
According to another feature, the anti-rotation device includes a
first lock which pivotally locks the first half-cradle on the
pylon, and a second lock which pivotally locks the second
half-cradle on the pylon.
According to another feature, the first half-cradle comprises a
slide connection which slidably links the first half-portion of the
O-type thrust reverser movable body on the pylon, and the second
half-cradle comprises a slide connection which slidably links the
second half-portion of the O-type thrust reverser movable body on
the pylon.
According to another feature, the thrust reverser includes a
plurality of actuators each linking the front frame of the thrust
reverser on the cascade vanes and which are designed so as to
slidably drive the assembly formed by the cascade vanes and the
O-type thrust reverser movable body.
The present disclosure also concerns a nacelle for an aircraft
turbojet engine including a thrust reverser of the previously
described type.
Further areas of applicability will become apparent from the
description provided herein. It should be understood that the
description and specific examples are intended for purposes of
illustration only and are not intended to limit the scope of the
present disclosure.
DRAWINGS
In order that the disclosure may be well understood, there will now
be described various forms thereof, given by way of example,
reference being made to the accompanying drawings, in which:
FIG. 1 is a rear perspective sectional view of a thrust reverser of
a D-type nacelle, according to the prior art;
FIG. 2 is a schematic side view illustrating a nacelle including an
O-type thrust reverser with a thrust reverser movable body in the
direct jet position, according to the teachings of the present
disclosure;
FIG. 3 is a schematic view similar to that of FIG. 2, illustrating
the O-type thrust reverser movable body of FIG. 2 in a thrust
reversal position;
FIG. 4 is a schematic cross-sectional view illustrating the first
half-portion of the O-type thrust reverser movable body of FIG. 2
in its closed position;
FIG. 5 is a schematic cross-sectional view illustrating the first
half-portion of the O-type thrust reverser movable body of FIG. 2
in its closed position and an outer cowl in the butterfly open
position;
FIG. 6 is a schematic cross-sectional view illustrating the first
half-portion of the O-type thrust reverser movable body of FIG. 2
in its butterfly open position;
FIG. 7 is a schematic cross-sectional view illustrating the O-type
thrust reverser movable body of FIG. 2 and the actuators for
slidably driving the O-type thrust reverser movable body;
FIG. 8 is a schematic longitudinal sectional view illustrating a
first half-cradle which links the first half-portion of the O-type
thrust reverser movable body on the suspension pylon, according to
the teachings of the present disclosure;
FIG. 9 is a schematic cross-sectional view illustrating the first
half-cradle and the first half-portion of the O-type thrust
reverser movable body in its closed position, according to the
teachings of the present disclosure;
FIG. 10 is a schematic cross-sectional view illustrating the first
half-cradle and the first half-portion of the O-type thrust
reverser movable body in its butterfly open position, according to
the teachings of the present disclosure;
FIG. 11 is a schematic longitudinal sectional view illustrating the
cascade vanes on the O-type thrust reverser movable body, which is
in the direct jet reversal position, according to the teachings of
the present disclosure;
FIG. 12 is a schematic view similar to that of FIG. 11 illustrating
the O-type thrust reverser movable body detached from the cascade
vanes, according to the teachings of the present disclosure;
FIG. 13 is a perspective view illustrating the assembly that is
removed during a turbojet engine removal operation, and which
comprises in particular the turbojet engine, the cascade vanes and
the actuators for driving the O-type thrust reverser movable body,
according to the teachings of the present disclosure; and
FIG. 14 is a perspective view illustrating the O-type thrust
reverser movable body comprising an outer cowl, and an inner wall
which delimits a cold air flow path with an inner structure which
surrounds the turbojet engine, according to the teachings of the
present disclosure.
The drawings described herein are for illustration purposes only
and are not intended to limit the scope of the present disclosure
in any way.
DETAILED DESCRIPTION
The following description is merely exemplary in nature and is not
intended to limit the present disclosure, application, or uses. It
should be understood that throughout the drawings, corresponding
reference numerals indicate like or corresponding parts and
features.
In the description and the claims, the terminology longitudinal,
vertical and transverse will be adopted in a non-limiting manner
with reference to the trihedron L, V, T indicated in the figures,
whose axis L is parallel to the axis of the nacelle.
In all of these figures, identical or similar reference numerals
represent identical or similar members or sets of members.
It should be noted that in the present patent application, the
terms "upstream" and "downstream" should be understood with respect
to the circulation of the air flow inside the propulsion unit
formed by the nacelle and the turbojet engine, that is to say from
left to right in FIG. 2.
In the present application, the terms "upper," "lower" and their
derivatives refer to the position or the orientation of an element
or a component, this position or this orientation being considered
when the nacelle is in the service configuration on an aircraft on
the ground.
In FIGS. 2 and 3, there is represented a nacelle 10 (for example,
for a turbojet engine nacelle) which has a substantially tubular
structure around a longitudinal central axis A.
The nacelle 10 comprises an air inlet 12 upstream of the turbojet
engine 14, a middle section 16 intended to surround a fan of the
turbojet engine, a downstream section 18 intended to surround the
combustion chamber of the turbojet engine 14, the nacelle 10
terminating in an ejection nozzle 20 whose outlet is located
downstream of the turbojet engine 14.
In addition, the downstream section 18 of the nacelle 10 includes a
cascade thrust reverser 22.
The thrust reverser 22 includes a front frame 24 which is mounted
downstream of the fan casing 26 and which supports thrust reverser
cascades 28.
Also, the thrust reverser 22 includes an O-type thrust reverser
movable body 30 which has a generally cylindrical shape around the
longitudinal central axis A of the nacelle 10.
As shown in FIGS. 7 and 14, the O-type thrust reverser movable body
30 comprises an outer cowl 32 and an inner wall 34 which is adapted
to delimit a cold air flow path 35 with an inner structure 36 which
surrounds the turbojet engine 14.
The inner structure 36 is formed by half-cowls which are adapted so
as to open in a butterfly fashion in order to allow access to the
turbojet engine 14.
The O-type thrust reverser movable body 30 is slidably mounted
along the longitudinal central axis A, between a direct jet
position illustrated in FIG. 2, in which the outer cowl 32 covers
the thrust reverser cascades 28, a thrust reversal position
illustrated in FIG. 3, in which the outer cowl 32 uncovers the
thrust reverser cascades 28.
To this end, as shown in particular in FIGS. 7 and 13, the thrust
reverser 22 includes four cylinder-type actuators 38 (two of which
are shown in FIG. 13), each linking the front frame 24 on a rear
frame of the thrust reverser cascades 28 and which are designed so
as to slidably drive the assembly formed by the thrust reverser
cascades 28 and the O-type thrust reverser movable body 30 between
its direct jet position and its thrust reversal position.
Also, the thrust reverser cascades 28 are linked on the O-type
thrust reverser movable body 30, so that the thrust reverser
cascades 28 are slidably driven with the O-type thrust reverser
movable body 30 by the actuators 38. For this purpose, the thrust
reverser cascades are slidably mounted on a guide track (not
shown).
More particularly, the rear frame of the thrust reverser cascades
28 is linked on the O-type thrust reverser movable body 30.
As shown in FIG. 11, the O-type thrust reverser movable body 30
carries flaps 39 which are pivotally mounted within the cold air
flow path 35, between a rest position illustrated in FIG. 11, which
corresponds to the direct jet position of the O-type thrust
reverser movable body 30, and a thrust reversal position (not
represented), which corresponds to the thrust reversal position of
the O-type thrust reverser movable body 30, in which the flaps 39
direct the air flow toward the thrust reverser cascades 28.
It should be noted that the thrust reverser 22, and the nacelle 10
in general, have a symmetrical design according to a plane P of
symmetry, illustrated in FIG. 7, which extends vertically through
the longitudinal central axis A of the nacelle 10.
The thrust reverser 22 comprises a cradle 40 which is partially
shown in FIGS. 4 to 10, and which is designed so as to link an
upper portion of the O-type thrust reverser movable body 30 on a
suspension pylon 42 of the nacelle 10 in particular in order to
provide sliding of the O-type thrust reverser movable body 30.
The cradle 40 includes a first half-cradle 44 and a second
half-cradle 46 shown in FIG. 7, which is arranged symmetrically to
the first half-cradle 44 and which is identical to the first
half-cradle 44.
For brevity purposes, only the first half-cradle 44 is described
later on.
Similarly, the O-type thrust reverser movable body 30 comprises a
first half-portion 48 and a second half-portion 50 each being
generally semi-cylindrical and are linked to one another in a lower
portion of the O-type thrust reverser movable body 30, by a first
dismountable link device 52.
The first dismountable link device 52 is of the screw-nut type.
Nonetheless, without limitation, the first dismountable link device
52 comprise a lock or any other known dismountable link device.
More particularly, the first dismountable link device 52 comprises
a first flange and a second flange which bear in vertical and
longitudinal planes and which are linked to one another by
screws.
The first half-portion 48 and the second half-portion 50 of the
O-type thrust reverser movable body 30 are generally identical by
symmetry according to the plane P of symmetry, so that only the
first half-portion 48 of the O-type thrust reverser movable body 30
is described later on.
Each of the first half-portion 48 and the second half-portion 50 of
the O-type thrust reverser movable body 30 are pivotally mounted
about a longitudinal pivot axis B, between a closed position
illustrated in FIGS. 7, 4 and 9 and a butterfly open position for
removing the turbojet engine 14, illustrated in FIGS. 6 and 10, via
the cradle 40.
To this end, the first half-cradle 44 carries the first
half-portion 48 of the O-type thrust reverser movable body 30, and
the first half-cradle 44 is pivotally mounted on the suspension
pylon 42 about the longitudinal pivot axis B, by three hinges 54
shown in FIG. 8, so as to provide pivoting of the first
half-portion 48 of the O-type thrust reverser movable body 30.
In addition, referring to FIGS. 4, 8 and 9, the first half-cradle
44 includes a longitudinal slide 56 which cooperates with a rail 58
secured to the O-type thrust reverser movable body 30, so as to
enable sliding of the O-type thrust reverser movable body 30
between its direct jet position and its thrust reversal
position.
In order to pivotally lock the first half-portion 48 and the second
half-portion 50 of the O-type thrust reverser movable body 30, in
their closed position, the thrust reverser 22 includes an
anti-rotation device 60 illustrated in FIGS. 9 and 10.
The anti-rotation device 60 includes a first lock 62 which
comprises a clevis 64 secured to the suspension pylon 42 and an
eyelet 66 secured to the first half-cradle 44.
In addition, a removable pin 68 cooperates with the eyelet 66 and
the clevis 64 so as to lock the first half-cradle 44 on the pylon,
removal of the pin 68 enables rotatably releasing the first
half-cradle 44.
By symmetry according to the plane P, the thrust reverser 22
includes a second lock 70 shown in FIG. 7 which pivotally locks the
second half-cradle 46 on the suspension pylon 42.
According to another aspect illustrated in FIG. 11, the thrust
reverser 22 includes a second dismountable link device 72 which
slidably links the thrust reverser cascades 28 on the O-type thrust
reverser movable body 30 in a dismountable manner.
The second dismountable link device 72 is of the screw-nut type.
Nonetheless, without limitation, the second dismountable link
device 72 comprises a lock or any other known dismountable link
device.
According to another aspect, the outer cowl 32 of the O-type thrust
reverser movable body 30 includes C-shaped first half-cowl 74 and
second half-cowl 76 each being pivotally mounted about a
longitudinal pivot axis C, between a closed position illustrated in
FIG. 4, and a maintenance butterfly open position, illustrated in
FIG. 5.
To this end, as shown in FIG. 8, the structure of the first
half-portion 48 of the O-type thrust reverser movable body 30
includes two hinges 78 which provide pivoting of the C-shaped first
half-cowl 74.
The thrust reverser 22 according to the present disclosure enables
a quick removal of the assembly formed by the turbojet engine 14,
the thrust reverser cascades 28 and the actuators 38 shown in FIG.
13.
For this purpose, a first step comprises sliding the O-type thrust
reverser movable body 30 rearward from its direct jet position
illustrated in FIG. 11, up to a removal position illustrated in
FIG. 12 in which the front edge 80 of the flaps 39 is cleared from
the diverting edge 82 during opening of the O-type thrust reverser
movable body 30 in a butterfly fashion.
In a second step, the second dismountable link device 72 which
slidably links the thrust reverser cascades 28 on the O-type thrust
reverser movable body 30 is dismounted so as to release the
assembly formed by the O-type thrust reverser movable body 30, the
cradle 40 and the flaps 39.
In a third step, the anti-rotation device 60 is unlocked so as to
pivotally release the first half-portion 48 and the second
half-portion 50 of the O-type thrust reverser movable body 30.
Finally, in a fourth step, the first half-portion 48 and the second
half-portion 50 of the O-type thrust reverser movable body 30 are
pivotally driven from their closed position, up to their butterfly
open position for removing the turbojet engine 14.
The prior description of the present disclosure is provided as a
non-limiting example.
Unless otherwise expressly indicated herein, all numerical values
indicating mechanical/thermal properties, compositional
percentages, dimensions and/or tolerances, or other characteristics
are to be understood as modified by the word "about" or
"approximately" in describing the scope of the present disclosure.
This modification is desired for various reasons including
industrial practice, material, manufacturing, and assembly
tolerances, and testing capability.
As used herein, the phrase at least one of A, B, and C should be
construed to mean a logical (A OR B OR C), using a non-exclusive
logical OR, and should not be construed to mean "at least one of A,
at least one of B, and at least one of C."
The description of the disclosure is merely exemplary in nature
and, thus, variations that do not depart from the substance of the
disclosure are intended to be within the scope of the disclosure.
Such variations are not to be regarded as a departure from the
spirit and scope of the disclosure.
* * * * *